Stability and Receptivity of the Swept-Wing Boundary-Layer Flow Controlled by a Periodic Sequence of Plasma Actuators

The process of flow control in the boundary layer on a swept wing using a span-periodic sequence of plasma actuators mounted at an angle to the leading edge is modeled. The stabilizing effect is investigated as a function of the angle of inclination of the actuators. The calculations of the oscillation component of the controlled flow are performed in the linear approximation in a small parameter, namely, the inverse Reynolds number. The possibility of the resonance flow response to the oscillation component of the action is found out, when the actuator directions are close to the direction of the external flow streamline.